Experimental and Numerical Analysis of the Aerodynamics and Vortex Interactions on Multi-Swept Delta Wings

The flow field around a generic multi-swept delta wing configuration is nvestigated under transonic flow conditions, both experimentally and numerically. A special focus is on the analysis of vortex/vortex- and vortex/shock-interactions at moderate angles of attack. In the present study, the Mach number is varied between Ma = 0.50 and Ma = 1.41 and the angle of attack (AoA) is varied between AoA = 8° and AoA = 28°. Numerical results are validated using experimental surface pressure data from pressure taps, as well as forces and moments based on strain gauge measurements. For selected cases, velocity field data from particle image velocimetry (PIV) measurements are available as well. Over a broad range of angle of attack and Mach number, strong vortex/vortex-interactions, including vortex-braiding and vortex-merging, occur. The location of vortex merging is moving downstream with increasing angle of attack and increasing Mach number. Additionally, at Ma = 0.85, vortex/shock interaction occurs above the wing. For moderate angles of attack, shock-induced vortex-breakdown is observed